Show that angular momentum of a satellite of mass `M_(s)` revolving around earth of mass `M_(e)` in an orbit of radius `r` is `sqrt(GM_(s)^(2)M_(e)r)`.
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A satellite revolues around earth under gravitaitonal pull which provides the necessary
centripetal force, i.e., `M_(S) = (upsilon^(2))/(r ) = (GM_(e)M_(s))/(r^(2))`
`upsilon = sqrt((GM_(e))/(r ))`
Angular momentum of satellite `L = M_(s). upsilon. r`
`L = M_(s) sqrt((GM_(e))/(r )) xx r = sqrt(GM_(s)^(2)M_(e) r)`